Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-foot Pressure Wind Tunnel II : The Effect of Constant-chord Leading- and Trailing-edge Flaps on the Low-speed Characteristics of the Wing

Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and a taper ratio of 0.50, equipped with leading- and trailing-edge flaps. The purpose of the tests was to determine the low-speed aerodynamic characteristics of the wing as affected by the separate or combined deflections of a full-span, constant-chord, leading-edge, plain flap and a partial-plan, constant-chord, trailing-edge flap of either the plain or split type. Results regarding the maximum lift characteristics, pitching-moment characteristics, drag coefficients, lift-drag ratio, and effect of Reynolds number and profile modification are provided.